X-Virus-Scanned: clean according to Sophos on Logan.com X-SpamCatcher-Score: 50 [XX] Return-Path: Received: from ms-smtp-03.southeast.rr.com ([24.25.9.102] verified) by logan.com (CommuniGate Pro SMTP 5.1.8) with ESMTP id 2024202 for flyrotary@lancaironline.net; Thu, 03 May 2007 16:53:42 -0400 Received-SPF: pass receiver=logan.com; client-ip=24.25.9.102; envelope-from=eanderson@carolina.rr.com Received: from edward2 (cpe-024-074-103-061.carolina.res.rr.com [24.74.103.61]) by ms-smtp-03.southeast.rr.com (8.13.6/8.13.6) with SMTP id l43KqTjo013026 for ; Thu, 3 May 2007 16:52:30 -0400 (EDT) Message-ID: <002d01c78dc5$25668d20$2402a8c0@edward2> From: "Ed Anderson" To: "Rotary motors in aircraft" References: Subject: Re: [FlyRotary] Re: Cooling area drag Date: Thu, 3 May 2007 16:53:47 -0400 MIME-Version: 1.0 Content-Type: multipart/mixed; boundary="----=_NextPart_000_0029_01C78DA3.9E03E6F0" X-Priority: 3 X-MSMail-Priority: Normal X-Mailer: Microsoft Outlook Express 6.00.2900.3028 X-MIMEOLE: Produced By Microsoft MimeOLE V6.00.2900.3028 X-Virus-Scanned: Symantec AntiVirus Scan Engine This is a multi-part message in MIME format. ------=_NextPart_000_0029_01C78DA3.9E03E6F0 Content-Type: multipart/alternative; boundary="----=_NextPart_001_002A_01C78DA3.9E03E6F0" ------=_NextPart_001_002A_01C78DA3.9E03E6F0 Content-Type: text/plain; charset="iso-8859-1" Content-Transfer-Encoding: quoted-printable Bob, that is going to be one sweet looking aircraft. If I judged = accurately from the photo your radiator is horizontal and I presume in = the duct/scoop I see forward of the lower Fire wall. If I visualize it = correctly the air enters the front of the scoop, makes a 90 degree turn = to go through your horizontal radiator and then makes another 90 degree = turn and goes out the top rear of the duct work - please confirm or = correct. I don't need to tell you that ideally, you would not want to make the = air do two 90 degree turns - but, we all face compromises with our = installations. I presume you already have your radiator? if not there = are possibly some significant things (if you are having a custom one = made ) regarding the orientation of the cooling fins to the air flow = that might be done. IF you had the core constructed such that the air = channels/fins were oblique to the plain of the radiator this would = greatly help the entry and exiting of the air through the core. But, I = will assume the air core channels are perpendicular to the plane of the = radiator as is commonly done. Given that is assumption is correct, then there are two approaches I can = think of.=20 One is as you so correctly surmise is to guide the air through its = turns and the core with a minimum of perturbation. However, if it is = not too late, I would strongly recommend that you incline your core in = the duct as much as you can. If appears from the photo that you have = sufficient depth to incline the radiator (assuming its width is the same = or smaller than the ducts) 20-35 degrees. If you could do that it would = help the air flow a great deal. By inclining your radiator (even a little bit would help quite a bit ), = I've attached a crude drawing of what I think your airflow/radiator = situation is and one that would be better. Let me know if this change = is feasible? Otherwise, we will work with what we have. Ed =20 ----- Original Message -----=20 From: bmears9413@aol.com=20 To: Rotary motors in aircraft=20 Sent: Thursday, May 03, 2007 4:00 PM Subject: [FlyRotary] Re: Cooling area drag Ed, Give me some pointers on my cooling system before I get started. You = surely will save me some mistakes. My air intake will be below and = behind my radiator. I imagined just building some deflectors to "s" the = air up to the radiator. Aft of the radiator the air will exit out the = back half of the air scoop. the radiator will be laying flat, under the = motormount. the oil coolers are under each wing...as it should be in s = spitfire. Thanks, Bob Mears Supermarine Spitfire =20 -----Original Message----- From: eanderson@carolina.rr.com To: flyrotary@lancaironline.net Sent: Thu, 3 May 2007 11:49 AM Subject: [FlyRotary] Re: Cooling area drag Actually, Mark, I started pulling together what I believed to be the = major factors without getting too down in the weeds about rotary = cooling, a couple of years ago with the intention of publishing an e = book (pamphlet more likely) . Then I ran into the problem that the = seemingly best diffuser (Streamline duct) was simply too long (in its = optimum configuration) for most of our needs. Yes, you can shorten it = but then you incur more drag. So I scratched my head about that for a = while until the light bulb came on. After experimenting with a number of duct shapes and reading more, I = came to the conclusion that if my understanding about what killed = effective cooling was correct then I should be able to achieve my = cooling/drag goals with the "Pinched" duct. But, what I wanted to do = and never took the time to do was to go back with Mr. Bernoulli and = calculate the air velocity along each segment of the streamline duct and = then do the same for my "pinched" duct to see if there was any = similarity. Also, I have not paid much attention to the exiting duct - = simply because I don't have room for one. I tired one back almost 8 = years ago and decided the zigs and zags it had to avoid = engine/motormount, etc impeded airflow more than helped it. But, alas, just as I was recently about to go to publication, the new = "bible" of cooling was published - so how could I possibly compete {:>). = I may still do it as if it passes the gauntlet of folks on this list = (or errors if any {:>)) are corrected,as it may be useful to some. Ed ----- Original Message -----=20 From: Mark Steitle=20 To: Rotary motors in aircraft=20 Sent: Thursday, May 03, 2007 12:34 PM Subject: [FlyRotary] Re: Cooling area drag ED, So, tell us, when is your book on cooling going to be available? =20 Mark =20 On 5/3/07, Ed Anderson wrote:=20 Less we forget how important drag is in our hobby, I took a = formula for calculating drag at different airspeeds and the Hp required = to push the given frontal area along at the stated airspeed.=20 This is for two of our traditional GM evaporator cores using their = combined frontal area of 180 sq inch or 1.25 sq feet. This assumes = that airspeed shown represents the velocity through the cooling core = (which is not really likely to reach speeds above 80 mph if you have any = sort of ducting), but that is an assumption on my part since as Bill = keeps reminding me I have not instrumented my ducts {:>)=20 Air Speed (MPH) HP =20 40 0.533333=20 60 1.80=20 80 4.27=20 120 14.40=20 140 22.87=20 160 34.13=20 180 48.60=20 200 66.67=20 Clearly the faster your cruise speed the more important it is to = minimize cooling drag. Of course the airspeed the core sees should = normally not be over 10% of your cruise speed or 30% of your climb speed = (According to Horners rule of thumb). So slowing down your cooling = airflow to lessen drag is one reason for paying some attention to your = ducting. However, cooling again depends on many other variables, for = instance accepting a high velocity airflow through your core may permit = you to use a smaller frontal area core thereby offsetting to some = extent the higher drag. In fact, space constraints may force you to his = configuration regardless.=20 Another factor to consider is trade off between frontal area drag = and thermal transfer efficiency. A large thin radiator is theoretical = the most efficient due to that factor. However, it disturbs a larger = segment of air (resulting in higher drag) - not really important in an = auto at 60 mph but very important in a Cozy at 200+ MPH. =20 A thicker core with smaller frontal area disturbs less air and = while it has more skin drag that is small compared to the frontal area = drag. Tracy refers to the approach of thicker cores as "... getting the = most cooling possible for the smallest column of air disturbed". So = while theoretically the thicker core is less thermodynamic efficient - = it turns out with sufficient dynamic pressure available it provides = definite benefits in our application. The average thickness of NASCAR = radiators is 3" and up to 7" for the longer high speed tracts. Since = they operate in speed regimes close to what most of us fly - they just = might know what they are doing given the $$ they will spend for even a = slight speed advantage.=20 Ok, back to creating a company - boy, a lot to learn Ed =20 Ed Anderson Rv-6A N494BW Rotary Powered Matthews, NC eanderson@carolina.rr.com=20 http://members.cox.net/rogersda/rotary/configs.htm#N494BW http://www.dmack.net/mazda/index.html -------------------------------------------------------------------------= ----- AOL now offers free email to everyone. Find out more about what's free = from AOL at AOL.com. ------=_NextPart_001_002A_01C78DA3.9E03E6F0 Content-Type: text/html; charset="iso-8859-1" Content-Transfer-Encoding: quoted-printable
Bob, that is going to be one sweet = looking=20 aircraft.  If I judged accurately from the photo your radiator is=20 horizontal and I presume in the duct/scoop I see forward of the lower = Fire=20 wall.  If I visualize it correctly the air enters the front of the = scoop,=20 makes a 90 degree turn to go through your horizontal radiator and then = makes=20 another 90 degree turn and goes out the top rear of the duct work - = please=20 confirm or correct.
 
I don't need to tell you that ideally, = you would=20 not want to make the air do two 90 degree turns - but, we all face = compromises=20 with our installations.   I presume you already have your=20 radiator?  if not there are possibly some significant things (if = you are=20 having a custom one made ) regarding the orientation of the cooling fins = to the=20 air flow that might be done.  IF you had the core constructed such = that the=20 air channels/fins were oblique to the plain of the = radiator  this=20 would greatly help the entry and exiting of the air through the = core.  But,=20 I will assume the air core channels are perpendicular to the plane of = the=20 radiator as is commonly done.
 
Given that is assumption is correct, = then there are=20 two approaches I can think of. 
 
 One is as you so correctly = surmise =20 is to  guide  the air through its turns and the core with = a=20 minimum of perturbation.  However, if it is not too late, I would = strongly=20 recommend that you incline your core in the duct as much as you = can.  If=20 appears from the photo that you have sufficient depth to incline the = radiator=20 (assuming its width is the same or smaller than the ducts) 20-35 = degrees. =20 If you could do that it would help the air flow a great = deal.
 
By inclining your radiator (even a = little bit would=20 help quite a bit ), I've attached a crude drawing of what I think = your=20 airflow/radiator situation is and one that would be better.  Let me = know if=20 this change is feasible?  Otherwise, we will work with what we=20 have.
 
Ed
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
----- Original Message -----
From:=20 bmears9413@aol.com
Sent: Thursday, May 03, 2007 = 4:00=20 PM
Subject: [FlyRotary] Re: = Cooling area=20 drag

Ed,
Give me some pointers on my cooling system before I get started. = You=20 surely will save me some = mistakes. My air=20 intake will be below and behind my radiator. I imagined just building some = deflectors to "s" the air up to the radiator. Aft of the radiator the = air will=20 exit out the back half of the air scoop. the radiator will be laying = flat,=20 under the motormount. the oil coolers are under each wing...as it = should be in=20 s spitfire.
Thanks,
Bob Mears
Supermarine Spitfire
 
 
 
 
 
-----Original Message-----
From:=20 eanderson@carolina.rr.com
To: flyrotary@lancaironline.net
Sent: = Thu, 3=20 May 2007 11:49 AM
Subject: [FlyRotary] Re: Cooling area = drag

Actually, Mark,  I started pulling = together what I=20 believed to be the major factors without getting too down in the weeds = about=20 rotary cooling, a couple of years ago with the intention of publishing = an e=20 book (pamphlet more likely) .  Then I ran into the problem that = the=20 seemingly best diffuser (Streamline duct) was simply too long (in its = optimum=20 configuration) for most of our needs.  Yes, you can shorten it = but then=20 you incur more drag.  So I scratched my head about that for a = while until=20 the light bulb came on.
 
After experimenting with a number of duct = shapes and=20 reading more, I came to the conclusion that if my understanding about = what=20 killed effective cooling was correct then I should be able to achieve = my=20 cooling/drag goals with the "Pinched" duct.  But, what I wanted = to do and=20 never took the time to do was to go back with Mr. Bernoulli and = calculate the=20 air velocity along each segment of the streamline duct and then do the = same=20 for my "pinched" duct to see if there was any similarity.   = Also, I=20 have not paid much attention to the exiting duct - simply because I = don't have=20 room for one.  I tired one back almost 8 years ago and decided = the zigs and zags it had to avoid = engine/motormount, etc impeded airflow more = than helped=20 it.
 
 
But, alas, just as I was recently about to go = to=20 publication, the new "bible" of cooling was published - so how could I = possibly compete {:>).  I may still do it as if it passes the = gauntlet=20 of folks on this list (or errors if any {:>)) are corrected,as it = may be=20 useful to some.
 
Ed
 
 
----- Original Message -----
From:=20 Mark Steitle
To: Rotary motors in = aircraft=20
Sent: Thursday, May 03, 2007 = 12:34=20 PM
Subject: [FlyRotary] Re: = Cooling area=20 drag

ED,
 
So, tell us, when is your book on cooling going to be = available? =20
 
Mark

 
On 5/3/07, Ed=20 Anderson <eanderson@carolina.rr.com&g= t;=20 wrote:=20
Less we forget how important drag is in = our hobby, I=20 took a formula for calculating drag at different airspeeds and the = Hp required to push the given = frontal area=20 along at the stated airspeed.
 
This is for two of our traditional GM = evaporator cores using their = combined=20 frontal area of  180 sq inch or=20 1.25 sq feet.  This = assumes that=20 airspeed shown represents the velocity through the cooling = core=20 (which is not really likely to reach speeds above 80 mph if you have any sort of = ducting), but=20 that is an assumption on my part since as Bill keeps reminding me = I have=20 not instrumented my ducts {:>)
 
Air Speed (MPH)
          HP=20
40
0.533333
60
1.80
80
4.27
120
14.40
140
22.87
160
34.13
180
48.60
200
66.67
 
 
Clearly the faster your cruise speed the = more=20 important it is to minimize cooling drag.  Of course the = airspeed the=20 core sees should normally not be over 10% of your cruise speed or = 30% of=20 your climb speed (According to Horners=20 rule of thumb).  So slowing down your cooling airflow to = lessen drag=20 is one reason for paying some attention to your ducting.  = However,=20 cooling again depends on many other variables, for instance = accepting a=20 high velocity airflow through your core may permit you to use a = smaller=20 frontal area  core thereby offsetting to some extent the = higher=20 drag.  In fact, space constraints may force you to his = configuration=20 regardless.
 
Another factor to consider is trade off = between=20 frontal area drag and thermal transfer efficiency.  A large = thin=20 radiator is theoretical the most efficient due to that = factor. =20 However, it disturbs a larger segment of air (resulting in higher = drag) -=20 not really important in an auto at 60 mph but very important in a Cozy at 200+ = MPH.  =20
 
A thicker core with smaller frontal = area=20 disturbs less air and while it has more skin drag that is small = compared=20 to the frontal area drag.  Tracy refers to the approach of = thicker=20 cores as "... getting the most cooling possible for the = smallest=20 column of air disturbed".  So while theoretically the thicker = core is=20 less thermodynamic efficient - it turns out with sufficient = dynamic=20 pressure available it provides definite benefits in our=20 application.   The average thickness of NASCAR radiators is 3" and up to 7" for the longer = high speed=20 tracts.  Since they operate in speed regimes close to what = most of us=20 fly - they just might know what they are doing given the $$ they = will=20 spend for even a slight speed advantage.
 
Ok, back to=20 creating a company - boy, a lot to learn
 
Ed
 
 
 
  
 
 
Ed Anderson
Rv-6A N494BW Rotary=20 Powered
Matthews, NC
eanderson@carolina.rr.com=20
http://members.cox.net/rogersda/rotary/configs.htm#N494BW
http://www.dmack.net/mazda/index.html


AOL now offers free email to everyone. Find out more about what's free = from=20 AOL at AOL.com.
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